Example 10.1A uniform supersonic airflow traveling at Mach 2.0 passes over a wedgeM2(Fig. 10E.1). An oblique shock, making an angle of 40° with the flow P= 20 kPaT=-10 °C0=40%direction, is attached to the wedge under these flow conditions. If the staticM 2.0pressure and temperature in the uniform flow are, respectively, 20 kPa and-10 °C, determine the static pressure and temperature behind the wave, theMach number of the flow passing over the wedge, and the wedge half-angle. Figure 10E.1:

Answered: Image /qna-images/answer/eb7b916d-360d-4b46-ad73-29c184a6a1e7.jpg

Example 10.1 A uniform supersonic airflow traveling at Mach 2.0 passes over a wedge M2 (Fig. 10E.1). An oblique shock, making an angle of 40° with the flow Pi 20 kPa direction, is attached to the wedge under these flow conditions. If the static T =-10 °C 0 40% M-2.0 pressure and temperature in the uniform flow are, respectively, 20 kPa and -10 °C, determine the static pressure and temperature behind the wave, the Mach number of the flow passing over the wedge, and the wedge half-angle. Figure 10E.1:

Example 10.1 A uniform supersonic airflow traveling at Mach 2.0 passes over a wedge M2 (Fig. 10E.1). An oblique shock, making an angle of 40° with the flow Pi 20 kPa direction, is attached to the wedge under these flow conditions. If the static T =-10 °C 0 40% M-2.0 pressure and temperature in the uniform flow are, respectively, 20 kPa and -10 °C, determine the static pressure and temperature behind the wave, the Mach number of the flow passing over the wedge, and the wedge half-angle. Figure 10E.1:

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

See similar textbooks

Similar questions

78. 5.23. Assume that a supersonic nozzle operating isentropically delivers air at an exit Mach number of 2.8. The entrance conditions are 180 psia, 1000.R, and near-zero Mach number. (a) Find the area ratio A3/A2 and the mass flow rate per unit throat area. (b) What are the receiver pressure and temperature? (c) If the entire diverging portion of the nozzle were suddenly to detach, what would the Mach number and mA be at/the new outlet?
section If the back pressure is low enough and the throat is sonic, the Mach number is more than I in a/an during flow in a convergent-divergent nozzle. 1. diverging X2. converging X 3. entry X 4. throat
A cylinder 4 ft in diameter is placed in an air stream where the free-stream velocity is 100 ft/s. 1/ What is the vortex strength required to place the stagnation points at 0= 45° and 0 = 135? Does the vortex rotate clockwise or counterclockwise? 2/ Given the freestream pressure of 1967 Ibf/ft? and freestream temperature of 68F, calculate the pressure at the stagnation points? Hint: first find the freestream density.
AERODYNAMICS 1. A uniform supersonic air flow at Mach 2.0 passes over a wedge. An oblique shock, making an angle of 40° with the flow direction, is attached to the wedge. If the static pressure and temperature in the freestream are 0.5 Pa and 0°C, determine: a. the deflection angle in degrees b. the pressure ratio c. the Mach number in the downstream region
Fresh air enters a converging nozzle with velocity 110 m/s at steady condition, one-dimensional and isentropic. The nozzle throat area 40 cm? and the back pressure 0.5 MPa. The ambient air condition at 1 MPa and 620°C. Assume that the Cp =1.005 kJ/kg.K and k=1.4. Calculate the air mass flow rate Converging Nozzle | Fresh air
A converging-diverging nozzle with an exit-to-sonic area ratio of Ae/A = 47, exhausts air from a high-pressure reservoir (T, = 270 K) to the back plane, where the pressure is fixed at p, = 1 atm [abs). The test section area is Aa = 0.06 m? and the reservoir has a volume of 50 m. a) Assume that the test is located immediately upstream of the exit and that the flow up to the exit is isentropic, what is the minimum stagnation pressure under which the tunnel will start? b) What is the test section pressure under these conditions?
3. Assume a supersonic flow with M=2, P=1 atm, and T=288 K that is deflected via 15° at a compression corner. Determine M, P, T, as well as PO and TO behind the associated oblique shock wave.
can you please find solution for this question
Need solutions for 8.5 and 8.6